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フィルム冷却を考慮した液酸・液水ロケットエンジン性能解析
https://jaxa.repo.nii.ac.jp/records/6168
https://jaxa.repo.nii.ac.jp/records/6168cd51b536-589c-4a64-b031-a0eacd87f034
名前 / ファイル | ライセンス | アクション |
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49212035.pdf (2.2 MB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | フィルム冷却を考慮した液酸・液水ロケットエンジン性能解析 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | フィルム冷却 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ロケットエンジン | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 数値解析 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ナビエ-ストークス方程式 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | LE-5サブスケールエンジン | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 質量分率 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 速度ベクトル | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | マッハ数分布 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 層流 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 乱流 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 速度分布 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | film cooling | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | rocket engine | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | numerical analysis | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Navier-Stokes equation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | LE-5 subscale engine | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | mass fraction | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | velocity vector | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Mach number distribution | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | laminar flow | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | turbulent flow | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | velocity distribution | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Numerical investigations of the film cooling effect on rocket engine performance | |||||
著者 |
坪井, 伸幸
× 坪井, 伸幸× 伊藤, 隆× 宮島, 博× Tsuboi, Nobuyuki× Ito, Takashi× Miyajima, Hiroshi |
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著者所属 | ||||||
宇宙航空研究開発機構 宇宙科学研究本部 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構 | |||||
出版者(英) | ||||||
出版者 | Japan Aerospace Exploration Agency (JAXA) | |||||
書誌情報 |
宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2005論文集 en : JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2005 巻 JAXA-SP-05-017, p. 209-214, 発行日 2006-02-28 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | LOX/LH2 subscale rocket nozzle flow fields are computationally simulated using three-dimensional compressible Navier-Stokes equations. The area ratio of the nozzle is 140 and film coolant hydrogen gases are injected from 30 film cooling holes which are distributed circumferentially at the area ratio of 13. The experimental nozzle throat Reynolds number indicates that the boundary layer of the nozzle is in its transition region as the size of the nozzle is small. Both the turbulent and laminar computations are carried out to investigate the effect of the boundary layer conditions to the nozzle performance. The computed results show that the structure of the separated flow down stream of the film cooling injection significantly changes between the turbulent and laminar conditions. Since clear difference in performance between the laminar and turbulent conditions are also shown, the computed result confirms that the experiment boundary layer condition is in its transition region. The nozzle wall temperature also influences the nozzle performance and the computed nozzle performance shows rather laminar flow performance when the film coolant temperature and the nozzle wall temperatures are set to be close. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1349-113X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA11984031 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0049212035 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: JAXA-SP-05-017 |